try something

‎ 
Aerospace propulsion

ATM owns a test facility to test small Hybrid Rocket Engines up to 10 kN thrust (SLS) with different complete rocket engines or combustion chambers (with or without optical access) using different types of fuels, but mainly with paraffin and N2O as oxidizer. The test engines are completely instrumented, with a separate control chamber from the engine test cell. A strong collaboration is existing with ONERA, Royal Military Academy of Belgium and UnB (Brasil) on this topic.


 

Aerospace plasmas

Atmospheric re-entry is characterised by a combination of complex physico-chemical phenomena including thermal and chemical non-equilibrium. Predictive simulations using detailed aerothermodynamics models are essential in order to study these phenomena and estimate the generated heat flux during the descent phase. These calculations provide verification of experimental campaigns in ground-testing facilities and are key to design flight experiments. The numerical simulation of non-equilibrium plasma flows surrounding spacecraft during re-entry conditions is a challenging problem because of several aspects: chemical and thermal non-equilibrium, the multi-scale character of the flow and the large number of species and reactions involved. At ATM we use data-driven and machine-learning techniques to reduce the computational time of these simulations.

Onglet contenu 2 gjddsksuefhuoewgfiuddhdhddjjdjddjdjjdjjjdj